EP2634379B1 - Compression Sleeve Seal - Google Patents

Compression Sleeve Seal Download PDF

Info

Publication number
EP2634379B1
EP2634379B1 EP13157037.6A EP13157037A EP2634379B1 EP 2634379 B1 EP2634379 B1 EP 2634379B1 EP 13157037 A EP13157037 A EP 13157037A EP 2634379 B1 EP2634379 B1 EP 2634379B1
Authority
EP
European Patent Office
Prior art keywords
seal
compression sleeve
sleeve seal
flanges
flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP13157037.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2634379A1 (en
Inventor
Matthew Stephen Casavant
Brett Darrick Klingler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2634379A1 publication Critical patent/EP2634379A1/en
Application granted granted Critical
Publication of EP2634379B1 publication Critical patent/EP2634379B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49863—Assembling or joining with prestressing of part

Definitions

  • This invention relates to a seal for containment of gas leakage across two opposed flanges of a pressure vessel structure such as a turbine casing. This invention also relates to a method of sealing a pressure vessel structure such as a gas turbine casing.
  • a gasket or seal is employed together with a flange connection to prevent a gas such as air from escaping through flange joints.
  • some flange joints are employed which are not capable of totally sealing an air leak and some quantity of escaping air is acceptable, particularly where the amount of escaping air does not deleteriously affect the overall system of which the air is a part.
  • Gas turbines ordinarily utilize an air compressor having a cylindrical casing enclosing a cylindrical bladed rotor therein. Air at atmospheric pressure is ducted into the compressor at one open end of the cylinder to be compressed by the rotating blades of the rotor interengaging with blades in the casing. Air at elevated pressure is taken from the opposite end of the casing to be directed to combustion and exhaust system regions of the gas turbine apparatus which operate at a lower pressure.
  • the compressor casing as well as intermediate parts of the casing between the compressor and the combustion system usually comprises a multipart arrangement of component sections suitably fastenered together with appropriate flanges.
  • US 2457073 describes a turbine cylinder joint including two halves having oppositely-facing lugs at opposite sides of joint, and clamping means bearing against the lugs causing the joint faces to engage under pressure.
  • the clamping means comprises a plurality of clamps, each including a pair of jaws having lug-engaging inner ends and a strut connecting the outer end portions of the jaws which have aligned openings between the strut and the inner ends thereof.
  • First and second tension members extend through the aligned openings, each member having one end thereof acting compressively on the respective jaws.
  • a compression member extends through the openings and compressively engages the other end of the second tension member, while a nut carried by the other end of the first tension member and compressively engages the compression member.
  • the present invention resides in a seal for a turbine casing and in a method of sealing a turbine casing as defined in the appended claims.
  • a turbine casing 2 may include two sections each having a flange 4, 6.
  • the flange 4 may be part of an upper half casing and the flange 6 may be part of a lower half casing.
  • the turbine casing may include more than two sections as shown in the drawings.
  • the turbine casing may be a compressor casing, intermediate parts of a casing between the compressor and the combustion system, and/or a turbine rotor casing. As shown in Fig. 9 a row of fasteners 16 and corresponding nuts 14 along the flanges 4, 6 retain the joined casing sections in a sealed relationship.
  • the flange 4 includes a bore 8 that includes a counterbore 10.
  • the flange 6 includes a bore 18 that includes a counterbore (not shown).
  • the flanges 4, 6 may be configured not to seal against one another radially inboard of the bores 8,18 and the bores 8, 18 may form a potential leak path.
  • a compression sleeve seal 12 is inserted into the bores 8, 18 of the flanges 4, 6 with a fastener 6, such as a stud or a bolt.
  • the compression sleeve seal 12 is longer than the counterbore-to-counterbore length and an end 20 of the compression sleeve seal 12 extends through the bores 8, 18 of the flanges 4, 6.
  • a nut 14 is provided on each end of the fastener 16. The nuts 14 are turned which places the fastener 16 in tension.
  • the nuts 14 are turned until they contact the ends 20 of the compression sleeve seal 12 which may sit slightly proud of the flange face.
  • the release of the fastener 16 from tension compresses the fastener 16 along its longitudinal axis and creates a primary seal between the nuts 14 and the flanges 4, 6.
  • the compression sleeve seal 12 extends out radially from its longitudinal axis to create a secondary seal against the bores 8, 18 of the flanges 4, 6 to seal the potential leak path.
  • the compression sleeve seal 12 may be a tube having ends 20 that are configured to concentrate the load applied to the flanges 4, 6 by the fasteners 12 and the nuts 14 and the deformation of the compression sleeve seal 12 through Poisson's effect.
  • the ends 20 of the compression sleeve seal 12 may be thinner than a middle portion of the compression sleeve seal 12 to provide a predetermined contraction 24 to the compressed ends 22 of the compression sleeve seal 12.
  • the compression sleeve seal 12 may be thinnest in regions in which the load and Poisson's effect are to be concentrated.
  • the outer diameter of the compression sleeve seal 12 may be machined to concentrate or direct the load and Poisson's effect. For example, patterns may be milled into the outer diameter of the compression sleeve seal 12.
  • a turbine casing 2 includes a first section having a flange 4 and a second section having a flange 6.
  • the flanges 4, 6 may be held together by horizontal joint pins 26 and sealed by compression sleeve seals 12 that form primary and secondary seals in the manner described above.
  • the turbine casing sections may be connected initially through the compression sleeve seals 12, fasteners 16, and nuts 14 at locations along the flange except for the locations of the two horizontal joint pins 26.
  • the horizontal joint pins 26 may then be inserted and the alignment of the flanges 4, 6 may be set.
  • the compression sleeve seals 12 and the fasteners 16 may then be inserted into the flanges 4, 6 at the two locations of the horizontal joint pins 26 and the horizontal joint pins 26 may be torqued to secure the turbine casing sections together.
  • the compression sleeve seal 12 may be formed of metal, for example steel (e.g. a Cr-Mo-V steel).
  • the material of the turbine casing may be, for example, steel (e.g. a Cr-Mo-V steel).
  • the use of the compression sleeve seal may allow sealing of the sections of the turbine casing without the use of gaskets and/or rope seal grooves which may have a complicated structure and/or tend to break off into the gas stream path.
  • the compression sleeve seal is also preloaded and does not rely on the gas flow to seat the seal, as is required in existing butterfly valves.
  • the compression sleeve seal also provides primary and secondary seals in the flange bores and does not require caps on the tops of the fasteners.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13157037.6A 2012-02-28 2013-02-27 Compression Sleeve Seal Not-in-force EP2634379B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/406,943 US9046004B2 (en) 2012-02-28 2012-02-28 Compression sleeve seal

Publications (2)

Publication Number Publication Date
EP2634379A1 EP2634379A1 (en) 2013-09-04
EP2634379B1 true EP2634379B1 (en) 2015-04-08

Family

ID=47757447

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13157037.6A Not-in-force EP2634379B1 (en) 2012-02-28 2013-02-27 Compression Sleeve Seal

Country Status (5)

Country Link
US (1) US9046004B2 (ja)
EP (1) EP2634379B1 (ja)
JP (1) JP2013177891A (ja)
CN (1) CN103291388A (ja)
RU (1) RU2013108683A (ja)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2837775B1 (en) * 2013-08-15 2016-03-30 ALSTOM Technology Ltd Fixation device for turbine and method for applying fixation
KR101733626B1 (ko) * 2014-01-15 2017-05-24 두산중공업 주식회사 고압 터빈의 수압시험장치 및 수압시험방법
US9573009B2 (en) * 2014-01-22 2017-02-21 Max Fire Training, Inc. Firefighting training unit

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2457073A (en) * 1946-11-07 1948-12-21 Westinghouse Electric Corp Turbine cylinder joint
GB718625A (en) 1952-02-11 1954-11-17 Babcock & Wilcox Ltd Improvements in flanged and bolted pipe joints
US4266752A (en) 1979-03-30 1981-05-12 Mcc Flowseal, A Unit Of Mark Controls Corporation Seal structure
US4398695A (en) 1981-12-29 1983-08-16 Mcc Flowseal Metal seal structure
US5253875A (en) * 1988-12-22 1993-10-19 General Electric Company Method for sealing a high pressure section of a gas turbine casing
JP2001221012A (ja) * 2000-02-10 2001-08-17 Toshiba Corp 蒸気タービンおよび発電設備
US20050012278A1 (en) * 2002-11-07 2005-01-20 Delange Richard W. Metal sleeve seal for threaded connections
US6896482B2 (en) * 2003-09-03 2005-05-24 General Electric Company Expanding sealing strips for steam turbines
DE102006007312B4 (de) * 2006-02-16 2013-10-10 Federal-Mogul Sealing Systems Bretten Gmbh Gehäuseteil mit Dichtfläche und Dichtung für Brennkraftmaschine
CH703430A1 (de) 2010-07-13 2012-01-13 Alstom Technology Ltd Verfahren zur Einstellung der Rotorlage bei einer Gasturbine oder Dampfturbine.

Also Published As

Publication number Publication date
EP2634379A1 (en) 2013-09-04
RU2013108683A (ru) 2014-09-10
US9046004B2 (en) 2015-06-02
CN103291388A (zh) 2013-09-11
JP2013177891A (ja) 2013-09-09
US20130224005A1 (en) 2013-08-29

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